U.S. patent application number 15/460055 was filed with the patent office on 2018-05-10 for geolunar shuttle.
The applicant listed for this patent is Robert Salkeld. Invention is credited to Robert Salkeld.
Application Number | 20180127114 15/460055 |
Document ID | / |
Family ID | 62066044 |
Filed Date | 2018-05-10 |
United States Patent
Application |
20180127114 |
Kind Code |
A1 |
Salkeld; Robert |
May 10, 2018 |
Geolunar Shuttle
Abstract
A vehicle and method enabling propulsive flight from the Earth's
surface to and from the Moon's surface returning to horizontal
Earth landing along an airstrip. This reusable geolunar shuttle
vehicle can employ external drop tanks, and function as the final
propulsive stage of a multi-stage vehicle which can be: 1)
expendable, reusable or party reusable; 2) ground-launched,
sea-launched, or air-launched; 3) single-launched or
multiple-launched with assembly/refueling en route. The geolunar
shuttle can employ axial or ventral propulsion using current
operational single-fuel engines or dual-fuel engines providing
enhanced system performance. The geolunar shuttle can be crewed or
not, and can be internally configured to carry personnel, cargo, or
a mix of both. The geolunar shuttle can optionally be used for low
earth orbit and far space, including Earth escape missions.
Inventors: |
Salkeld; Robert; (Santa Fe,
NM) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Salkeld; Robert |
Santa Fe |
NM |
US |
|
|
Family ID: |
62066044 |
Appl. No.: |
15/460055 |
Filed: |
March 15, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64G 1/402 20130101;
B64G 1/007 20130101; B64G 1/002 20130101; B64G 1/005 20130101; B64G
1/646 20130101; B64G 1/14 20130101; B64G 1/62 20130101; B64G 1/401
20130101 |
International
Class: |
B64G 1/14 20060101
B64G001/14; B64G 1/40 20060101 B64G001/40; B64G 1/62 20060101
B64G001/62; B64G 1/00 20060101 B64G001/00 |
Claims
1. A method for performing spaceflight, the method comprising:
launching a reusable vehicle for traveling to the moon and
returning to earth on a first launcher; launching pre-filled
propellant tanks on a second launcher; and combining the vehicle
and the propellant tanks in or beyond earth orbit.
2. The method of claim 1 wherein the combining step is performed in
low earth orbit (LEO) or moon transfer orbit (MTO).
3. The method of claim 1 wherein the amount of propellant in the
propellant tanks is sufficient to enable the vehicle to land on the
moon's surface, lift off from the moon's surface, and return to the
earth's surface without refueling.
4. The method of claim 1 further comprising throttling throttleable
engines of the vehicle during lunar descent.
5. The method of claim 1 comprising the vehicle landing in a
horizontal attitude on the moon and/or earth using ventral
propulsion.
6. The method of claim 1 wherein the vehicle is ventrally propelled
for moon takeoff and landing, and axially propelled for injection
into MTO.
7. The method of claim 1 comprising operating dual fuel engines in
reverse use mode.
8. The method of claim 1 comprising landing the vehicle on
skids.
9. The method of claim 1 wherein the first launcher and/or the
second launcher comprises a Delta IV Heavy Launcher.
10. A vehicle for landing on and taking off from the moon, the
vehicle comprising dual fuel engines operated in reverse use
mode.
11. The vehicle of claim 10 comprising external tanks capable of
holding sufficient propellant to enable the vehicle to land on the
moon's surface, take off from the moon's surface, and return to the
earth's surface.
12. The vehicle of claim 10 comprising one or more throttleable
engines and a controllable throttling system.
13. The vehicle of claim 10 launchable from a Space Launch System
(SLS), a reusable global launcher, an air launch platform, or a sea
launch platform.
14. The vehicle of claim 10 wherein the vehicle is the payload of a
two stage expendable launch vehicle.
15. The vehicle of claim 10 comprising ventral propulsion for
horizontal attitude landing on the moon and/or earth.
16. The vehicle of claim 10 ventrally propelled for moon takeoff
and landing, and axially propelled for injection into MTO.
17. The vehicle of claim 10 comprising skids for landing.
18. A vehicle for use as a booster, the vehicle comprising an
aircraft launchable at sea, the aircraft having sufficient thrust
to provide a 45.degree. launch for a payload at an altitude greater
than 30,000 feet.
19. The vehicle of claim 18 comprising pontoons sufficient to
provide flotation for a seaplane weighing over four million
pounds.
20. The vehicle of claim 18 comprising one or more rocket
engines.
21. The vehicle of claim 20 comprising three tail-mounted RD-180
rocket engines.
22. The vehicle of claim 18 configured to be fueled and serviced
from shipborne or submarine facilities.
23. The vehicle of claim 18 wherein the payload comprises a
spacecraft, a geolunar shuttle, a ballistic missile, a cruise
missile, or a drone.
Description
BACKGROUND OF THE INVENTION
Field of the Invention (Technical Field)
[0001] Embodiments of the present invention are related to reusable
rocket vehicle systems to perform shuttle missions between the
surfaces of the Earth and the Moon.
BACKGROUND OF THE INVENTION
[0002] Note that the following discussion refers to a number of
publications and references. Discussion of such publications herein
is given for more complete background of the scientific principles
and is not to be construed as an admission that such publications
are prior art for patentability determination purposes.
[0003] The term geolunar shuttle means a reusable vehicle to carry
cargo from the Earth's surface to and from the Moon's surface.
Previous designs for geolunar shuttles include: 1) axial
tail-sitting Moon landing propulsion (egress/access awkward); 2)
all oxygen/hydrogen propulsion (hydrogen boiloff problem during
Moon surface stay-time); 3) assembly/refueling in low-Earth orbit
(performance penalty).
SUMMARY OF THE INVENTION
[0004] An embodiment of the present invention is a method for
performing spaceflight, the method comprising launching a reusable
vehicle for traveling to the moon and returning to earth on a first
launcher; launching pre-filled propellant tanks on a second
launcher; and combining the vehicle and the propellant tanks in or
beyond earth orbit. The combining step is preferably performed in
low earth orbit (LEO) or moon transfer orbit (MTO). The amount of
propellant in the propellant tanks is preferably sufficient to
enable the vehicle to land on the moon's surface, lift off from the
moon's surface, and return to the earth's surface without
refueling. The method preferably further comprises throttling
throttleable engines of the vehicle during lunar descent. The
method optionally comprises the vehicle landing in a horizontal
attitude on the moon and/or earth using ventral propulsion. The
vehicle is optionally ventrally propelled for moon takeoff and
landing, and axially propelled for injection into MTO. The method
preferably comprises operating dual fuel engines in reverse use
mode and optionally comprises landing the vehicle on skids. The
first launcher and/or the second launcher optionally comprise a
Delta IV Heavy Launcher.
[0005] Another embodiment of the present invention is a vehicle for
landing on and taking off from the moon, the vehicle comprising
dual fuel engines operated in reverse use mode. The vehicle
preferably comprises external tanks capable of holding sufficient
propellant to enable the vehicle to land on the moon's surface,
take off from the moon's surface, and return to the earth's
surface. The vehicle preferably comprises one or more throttleable
engines and a controllable throttling system. The vehicle is
preferably launchable from a Space Launch System (SLS), a reusable
global launcher, an air launch platform, or a sea launch platform.
The vehicle is optionally the payload of a two stage expendable
launch vehicle. The vehicle optionally comprises ventral propulsion
for horizontal attitude landing on the moon and/or earth. The
vehicle is optionally ventrally propelled for moon takeoff and
landing, and axially propelled for injection into MTO. The vehicle
optionally comprising skids for landing.
[0006] Another embodiment of the present invention is a vehicle for
use as a booster, the vehicle comprising an aircraft launchable at
sea, the aircraft having sufficient thrust to provide a 45.degree.
launch for a payload at an altitude greater than 30,000 feet. The
vehicle preferably comprises pontoons sufficient to provide
flotation for a seaplane weighing over four million pounds. The
vehicle preferably comprises one or more rocket engines, optionally
three three tail-mounted RD-180 rocket engines. The vehicle is
preferably configured to be fueled and serviced from shipborne or
submarine facilities. The payload optionally comprises a
spacecraft, a geolunar shuttle, a ballistic missile, a cruise
missile, or a drone.
[0007] Objects, advantages and novel features, and further scope of
applicability of the present invention will be set forth in part in
the detailed description to follow, taken in conjunction with the
accompanying drawings, and in part will become apparent to those
skilled in the art upon examination of the following, or may be
learned by practice of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] The accompanying drawings, which are incorporated into and
form a part of the specification, illustrate one or more
embodiments of the present invention and, together with the
description, serve to explain the principles of the invention. The
drawings and the dimensions therein are only for the purpose of
illustrating certain embodiments of the invention and are not to be
construed as limiting the invention.
[0009] In the drawings:
[0010] FIG. 1A shows an axially propelled geolunar shuttle of the
present invention comprising external propellant tanks. FIG. 1B
shows replacing the payloads of two upgraded Delta IV Heavy Earth
launchers with the geolunar shuttle detailed in FIG. 1A and
external fuel tanks, which rendezvous in Moon transfer orbit (MTO),
which is any transfer orbit that enables a space vehicle to reach
the moon, or any other orbit beyond earth orbit, for assembly of
the shuttle and the propellant tanks during the approximately
four-day transit from Earth to the Moon. The Earth-Moon
surface-Earth cargo is 4 people plus 1.5 tons. The gross liftoff
weight of the top launcher is 989 tons; the gross liftoff weight of
the bottom launcher is 816 tons.
[0011] FIG. 2A shows a ventrally propelled geolunar shuttle of the
present invention, comprising external propellant tanks. FIG. 2B
shows the geolunar shuttle and external tanks of FIG. 2B replacing
the payloads of two upgraded Delta IV Heavy Earth launchers, which
rendezvous in low Earth orbit (LEO) (220 nautical miles) for
assembly of the shuttle and the propellant tanks before injection
into MTO. The gross liftoff weight of the top launcher is 920 tons;
the gross liftoff weight of the bottom launcher is 967 tons.
[0012] FIG. 3A shows a ventrally propelled geolunar shuttle of the
present invention. FIG. 3B shows the shuttle replacing the payload
of a Space Launch System (SLS) Earth launcher having a gross
liftoff weight of 3215 tons for direct unrefueled geolunar shuttle
flight. The cargo for Earth-Moon surface-Earth travel is 4 people
plus 1 ton.
[0013] FIG. 4A shows a geolunar shuttle of the present invention
axially propelled for injection into MTO, and ventrally propelled
for Moon landing and takeoff (MLTO), for direct unrefueled geolunar
shuttle flight. FIG. 4B shows the shuttle replacing the SLS upper
stage and payload. The SLS has a gross liftoff weight of 3254 tons.
The cargo for Earth-Moon surface-Earth travel is 6 people plus 4
tons. FIG. 4C shows an axially propelled adaptation (detailed in
the inset of FIG. 4A) replacing the upper stage and payload of a
standard Delta IV Heavy Earth launcher having a gross liftoff
weight of 835 tons for LEO shuttle missions. The cargo for
Earth-LEO-Earth travel is 2 people plus 10 tons.
[0014] FIG. 5A shows a geolunar shuttle of the present invention
that is ventrally propelled for an entire personnel-plus-cargo
geolunar shuttle mission. FIG. 5B shows the shuttle replacing the
SLS Earth launcher upper stage and payload, resulting in a gross
liftoff weight of 3246 tons. The cargo for Earth-Moon surface-Earth
travel is 6 people plus 5 tons. FIG. 5C shows a cargo only version
(detailed in the inset of FIG. 5A) having a crew of two. In this
embodiment the gross liftoff weight is 3252 tons and the cargo for
Earth-Moon surface-Earth travel is 2 people round trip plus 11 tons
one way.
[0015] FIG. 6A shows a ventrally propelled embodiment of the
present invention similar to that shown in FIGS. 2 and 3 as the
payload of a two-stage expendable launch vehicle, for air launch
from a large subsonic landplane (see U.S. Pat. No. 9,139,311,
incorporated herein by reference). The main tank has a diameter of
27.5 feet and rocket-assisted pullup is used (launch at 60,000 ft.
altitude, 45.degree. flight path angle). FIG. 6B shows a reference
aircraft.
[0016] FIG. 7A shows the concept of FIG. 6A modified for subsonic
seaplane air launch. The rolling gear pods of the previous
configuration preferably contain sufficient volume so that they can
be modified as shown to pontoons to provide flotation for a 4.4
million lb. seaplane. FIG. 7B shows a reference aircraft.
[0017] FIGS. 8A and 8B show rocket engine scale and engine cycle
schematics respectively for mixed-mode, dual-fuel, tripropellant
engine designs.
[0018] FIG. 9A shows a dual fuel ventrally propelled embodiment of
the present invention comprising external propellant tanks. FIG. 9B
shows the shuttle and external tanks replacing the payloads of two
upgraded A IV Heavy Earth launchers. The top launcher has a gross
liftoff weight of 972 tons and the bottom launcher has a gross
liftoff weight of 816 tons. The Earth-Moon surface-Earth cargo is 4
people plus 1 ton.
[0019] FIG. 10A shows a ventrally propelled, fully reusable
embodiment of the present invention for personnel transport. FIG.
10B shows the shuttle as the payload of a reusable global launcher
(RGL) as described in U.S. Pat. No. 9,139,311. The gross liftoff
weight of the RGL is 3803 tons and the Earth-Moon surface-Earth
cargo is 6 people plus 1000 lbm.
[0020] FIG. 11A shows an embodiment of the present invention for
heavy end-load cargo transport. FIG. 11B shows the shuttle as the
payload of a RGL. The gross liftoff weight of the RGL is 5279 tons
and the Earth-Moon surface-Earth cargo is 2 people plus 17 t.
DETAILED DESCRIPTION OF THE INVENTION
[0021] Embodiments of the present invention are vehicles for
transporting personnel and/or cargo from Earth's surface to and
from the Moon's surface and return to Earth. The vehicle of the
present invention may or may not carry an onboard operating crew
and the cargo may or may not include personnel, and is preferably
capable of Earth return by horizontal airstrip landing. The
geolunar shuttle vehicle is preferably configured with high
fineness ratio of 7-8 for hypersonic lift-to-drag of 3-4 for
maneuvering escape re-entry and horizontal airstrip landing, as
described in U.S. Pat. Nos. 5,090,692 and 8,534,598, incorporated
herein by reference. Embodiments of the present invention comprise
ventral propulsion for both Moon landing/ascent and main Earth-Moon
transfer; dual-fuel (oxygen/hydrocarbon/hydrogen) Moon
landing/ascent as well as main Earth-Moon transfer propulsion;
reverse use of dual-fuel Moon landing/liftoff engines to eliminate
hydrogen boiloff during Moon surface stay; assembly/refueling
during Earth-Moon transfer (3-4 days) in Moon transfer orbit (MTO);
skid-type gear for both vertical Moon landing and horizontal Earth
airstrip landing; and conversion to seaplane capability for air
launch to expand launch flexibility. This combination has the
benefits of increased performance, flexibility and reusability
using existing rocket and turbofan engines; and further increased
performance, flexibility and reusability using designed dual-fuel
liftoff and space rocket engines.
[0022] The above proposed innovations can be incorporated into
geolunar shuttle concepts which can vary widely, depending on, for
example, Earth launcher, shuttle size, propulsion mode, propulsion
vector, location of any in-space assembly/refueling, and/or
manifest (e.g. manned/unmanned and/or cargo). These particular
examples, and specific options within each of them, can be treated
as ordinates of a seven-dimensional concept matrix having thousands
of meaningful cells, as exemplified in Table 1.
TABLE-US-00001 ORDINATE OPTIONS SUBOPTIONS Earth Launcher Ground
Launch (3) Delta IV Heavy (.DELTA.IVH) (3 + 2 = 5) Space Launch
System (SLS) Reusable Global Launcher (RGL- see 9, 139, 311) Air
Launch (2) Landplane Seaplane Size Replace Payload (P/L) (1) -- (1
+ 1 = 2) Replace Upper Stage + P/L (1) Propulsion Mode Single-fuel
(1) -- (1 + 2 = 3) Dual-fuel (2) Two single-fuel engines Dual-fuel
engines Propulsion Vector Axial (1) -- (1 + 2 + 1 = 4) Ventral (2)
Moon landing/take off (MLTO) Main including MLTO Axial + Ventral
(1) -- Assembly Location None (1) -- (1 + 5 = 6) Multiple (5) Low
Earth Orbit (LEO) Moon Transfer Orbit (MTO) LaGrange 1 (L-1)
Low-Moon Orbit (LMO) Moon surface (MS) Refueling Location As above
for Assembly Location (1 + 5 = 6) Manifest Multiple (3) Personnel
only (3) Personnel + Cargo Cargo only (unmanned)
[0023] Ten geolunar shuttle concepts are presented herein to
illustrate the diversity in this kaleidoscope of possibilities. Of
the ten geolunar shuttle concepts shown, the first seven use rocket
and turbofan engines which are operational (RS-25; RS-68; RL-10;
GEM-60; GE90-115 B) or substantially developed (J 2X; RL and
MB-60). The last three use dual-fuel engines which have been
designed but not developed, a space engine (O.sub.2/MH/H.sub.2) and
an Earth liftoff engine (O.sub.2/C.sub.3H.sub.8/H.sub.2).
[0024] Embodiments of the present invention comprise ventral
propulsion, as shown in FIGS. 1-7 and 9-11, which can be employed
not only for Moon landing and take-off, but also as main propulsion
for final Earth ascent and injection into Moon transfer orbit
(MTO). The total thrust of the ventral engines, which produce
thrust substantially perpendicular to the axis of the shuttle, at
ignition is as required to provide at least a 0.2 thrust: vehicle
weight ratio, considered adequate after clearance of most of the
atmosphere during Earth ascent, and more than adequate for vertical
Moon landing and take-off. The benefits of ventral propulsion
geometry are: 1) more surface area for propulsion than for
tail-mounted engines; 2) more engines for engine-out capability; 3)
horizontal attitude Moon landing for safer, more efficient Moon
surface access, for personnel and/or cargo; and 4) more forward
vehicle center of gravity for improved aerodynamic stability at
Earth re-entry and landing.
[0025] Propellant feed for ventral propulsion can be accomplished
by slight canting of the tanks, slosh baffles, and proper design at
the end of the tank, of a collecting sump to deliver the
propellants to the engines.
[0026] Embodiments of the present invention comprise a plurality of
Moon landing and takeoff engines, preferably about three or four,
considered reasonable in view of the fact that the Apollo program
(1969-1973) accomplished six geolunar shuttle missions with only
one Moon landing/takeoff engine. Also the availability of multiple
shuttle engines confers flexibility to correct for engine-out
situations by differential thrust through appropriate engine
throttling.
[0027] Embodiments of the present invention are assembled/refueled
in Moon transfer orbit (MTO), as shown in FIGS. 1 and 9. This
confers at least four new benefits: 1) elimination of the
performance penalties incurred by injection into rendezvous, and
ejection from LEO; 2) elimination of time spent in LEO during which
the far space shuttle is vulnerable to simple inexpensive ground
fire; 3) reduction of geolunar trip time and associated life
support and power weight requirements; and 4) simplification,
reliability and safety improvement for the overall transportation
mission.
[0028] Performance and configurations of the Delta IV Heavy launch
and its upgrades, shown in FIGS. 1, 2, 4, and 7 are known.
Currently operational Delta IV Heavy launch complexes on both
Atlantic and Pacific U.S. coasts could, with suitable
modifications, enable synchronized launches of upgraded vehicles
for assembly in LEO or MTO as shown in FIGS. 2, 1, and 9
respectively. The vehicle parameters for the embodiments shown in
FIGS. 1A, 2A, 3A, 4A, and 5A are listed in Tables 2-6,
respectively.
TABLE-US-00002 TABLE 2 VEHICLE ELEMENT VEHICLE ELEMENT EXTERNAL
TANKS PARAMETER CORE AT MTO AT LAUNCH Personnel (4) 1,000 -- --
ECLSS (10 days) 2,000 -- -- Mission equipment 3,000 -- -- Gross
start weight, lbm 55,800 30,900 51,500 Dry weight, lbm 17,000.sup.a
1,200 2,000 Engines 3xRL10( = 77) -- -- Re-entry planform loading,
28.7 (w/4 crew), lbm ft.sup.2 Re-entry cross range, n mi. .+-.4,500
-- -- .sup.aIncl. 15% margin
TABLE-US-00003 TABLE 3 VEHICLE ELEMENT VEHICLE ELEMENT EXTERNAL
TANKS PARAMETER CORE TOP (2) SIDE (2) Personnel (4) 1,000 -- --
ECLSS (10 days) 2,000 -- -- Mission equipment 2,000 -- -- Gross
start weight, lbm 54,300 30,600 96,100 Dry weight, lbm 17,500.sup.a
1,200 3,800 Engines 4xRL10( = 77) -- -- Re-entry planform loading,
26.8 -- -- (w/4 crew), lbm ft.sup.2 Re-entry cross range, n mi.
.+-.4,500 -- -- .sup.aIncl. 15% margin
TABLE-US-00004 TABLE 4 VEHICLE ELEMENT VEHICLE ELEMENT EXTERNAL
PARAMETER CORE TANKS Personnel (4) 1,000 -- ECLSS (10 days) 2,000
-- Mission equipment 2,000 -- Gross start weight, lbm 54,300 30,600
Dry weight, lbm 17,500.sup.a 1,200 Engines 4xRL10( = 77) --
Re-entry planform landing, 26.8 -- (w/4 crew), lbm ft.sup.2
Re-entry cross range, n mi. .+-.4,500 -- .sup.aIncl. 15% margin
TABLE-US-00005 TABLE 5 VEHICLE MOON LANDER SHUTTLE WITH SLS
LEO.sup.a SHUTTLE WITH PARAMETER CORE EXT. TANKS .DELTA. IV HEAVY
Personnel (6: 2) 1,500 -- 500 Env. contr/life support (10 days),
lbm 3,000 -- 1,000 Cargo, round trip 7,300 -- 19,400 Gross start
mass, lbm 223,800 524,900 157,400 Dry mass less cargo, lbm
53,500.sup.b 21,100 41,800.sup.b Engine (s) RL(orMB)-60 3 -- --
RL10( = 77) 4 -- -- RL10B-2 -- -- 2 Re-entry planform landing 23 --
2.5 (RT cargo), lbm/ft.sup.2 Cargo bay, ft 12 .times. 18 -- 12
.times. 30 Cargo density (RT), lbm/ft.sup.3 3.6 -- 7.9 Re-entry
cross range, n mi. .+-.4,500 -- .+-.4,500 .sup.a220 n mi.;
28.7.degree. .sup.bIncl. 15% margin
TABLE-US-00006 TABLE 6 VEHICLE CORE VEHICLE EXTERNAL PARAMETER
PERS. + CARGO CARGO TANKS Personnel (6; 2) 1,500 500 -- Env.
contr/life support (10 days), lbm 3,000 1,000 -- Cargo, lbm 9,300
22,400 -- Gross start mass, lbm 224,600 234,300 515,600 Dry mass
less cargo, lbm 52,900* 49,700 20,600 Engine RL(orMB)-60 2 2 --
RL10B-2 2 2 -- Re-entry planform loading, lbm ft.sup.2 23 16 --
Cargo bay, ft 15 .times. 18 15 .times. 30 -- Cargo density,
lbm/ft.sup.3 2.9 (RT).sup.a 3.8 (OW).sup.b -- Re-entry cross range,
n mi. .+-.4,500 .+-.4,500 -- *Incl. 15% margin .sup.around trip
.sup.bone way up
[0029] For the air-launch concepts shown in FIGS. 6 and 7,
airbreathing takeoff thrust is preferably provided by eight
GE90-115B turbofan engines each of which can produce a maximum sea
level thrust of 122,965 lbf. For seaplane takeoff this can be
augmented by the three tail-mounted RD-180 rocket engines as shown
in FIG. 7, each of which can provide a sea level thrust of 859,800
lbf. Advantages of seaplane operations include not being limited to
a few very large heavy-rated airstrips, and flexibility to be
fueled and serviced from shipborne facilities across global
locations, permitting a wide freedom of launch azimuths and orbital
inclinations. When a seaplane is used as a booster, the seaplane
preferably comprises adequate thrust to provide a zoom or pullup
launch for the shuttle payload at high altitude. For example, at an
altitude of approximately 30,000-40,000 feet (or even as high as
60,000-70,000 feet) the shuttle rocket engines (primary purpose)
are ignited, then, if it is not already, the booster orients itself
into a 45 degree attitude to launch the shuttle in a 45 degree
flight path.
[0030] Furthermore, the seaplane can rendezvous with a submarine as
well as a surface ship. If the seaplane as well as its payload is
fueled at the rendezvous, it could then proceed to make a launch
from any point on Earth, at any azimuth, regardless of diplomatic
over flight restrictions if on a military mission. The rendezvous
ship, or submarine, can transport all of the launch propellant,
seaplane fuel, electronics and personnel needed to support and
control a space launch, and confining these resources to shipboard
should substantially reduce the "bottom of the iceberg" of
infrastructure costs inevitably associated with the bureaucratic
sprawl of land-based space launch complexes. The seaplane can be of
any size and be used as a booster for less energetic missions than
space launch, such as a mobile launch platform for ballistic or
cruise missiles, or drones. Such a booster could also be used for
space missions other than lunar landing and return. Vehicle
parameters for the embodiments shown in FIGS. 6-7 are listed in
Tables 7-8 respectively.
TABLE-US-00007 TABLE 7 GLS BOOSTER GEOLUNAR Diameter: 27.5 pt.
SHUTTLE PARAMETER AIRCRAFT STAGE 1 STAGE 2 GLS Nominal payload, lbm
2,200,00 -- -- -- Crew 7 -- -- 4 (10 days) Cargo, lbm -- -- --
.sup. 2,000.sup.a Gross liftoff mass, lbm 4,400,000 1,714,800
403,200 83,900 Dry mass less engines, lbm 1,217,100 139,000 28,200
16,700.sup.b Engines, lbm 8xGE90-115B 154,520 -- -- -- 3xRD-180
37,715 -- -- -- 6xRS-25D -- 46,464 -- -- 4XRL(MB)-60 -- -- 4,400 --
4xRL10(.epsilon. = 77) -- -- -- 1,500 Re-entry planform loading,
lbm/ft.sup.2 -- -- -- 26.8 Cargo bay, ft -- -- -- 8 .times. 10
Cargo density, lb/ft.sup.3 -- -- -- 8.0 Re-entry crossrange, n mi.
-- -- -- .+-.4,500 .sup.aRoundtrip: Earth--Moon surface--Earth
.sup.bIncl. 15% margin
TABLE-US-00008 TABLE 8 GLS BOOSTER GEOLUNAR Diameter: 27.5 pt
SHUTTLE PARAMETER AIRCRAFT STAGE 1 STAGE 2 GLS Nominal payload, lbm
2,200,200 -- -- -- Crew 7 -- -- 4 (10 days) Cargo, lbm -- -- --
.sup. 2,000.sup.a Gross liftoff mass, lbm 4,400,000 1,714,800
403,200 83,900 Dry mass less engines, lbm 1,217,100 139,000 28,200
16,700.sup.b Engines, lbm 8xGE90-115B 154,520 -- -- -- 3xRD-180
37,715 -- -- -- 6xRS-25D -- 46,464 -- -- 4XRL(MB)-60 -- -- 4,400 --
4xRL10(.epsilon. = 77) -- -- -- 1,500 Re-entry planform loading,
lbm/ft.sup.2 -- -- -- 26.8 Cargo bay, ft -- -- -- 8 .times. 10
Cargo density, lb/ft.sup.3 -- -- -- 8.0 Re-entry crossrange, n mi.
-- -- -- .+-.4,500 .sup.aRoundtrip: Earth-Moon surface-Earth
.sup.bIncl. 15% margin
Dual Fuel Embodiments
[0031] FIGS. 8A and 8B show rocket engine scale and engine cycle
schematics respectively for mixed-mode, dual-fuel, tripropellant
engine designs. Design data for these engines is listed in Table
9.
TABLE-US-00009 TABLE 9 ENGINE DUAL EXPANDER COMMON INJECTOR MODE 1
MODE 2 PARAMETER O.sub.2/MMH/H.sub.2 H.sub.2 VERSION
(O.sub.2/C.sub.3H.sub.8/H.sub.2) (O.sub.2/H.sub.2) Thrust, sea
level, lbf N/A N/A 666,700 N/A Thrust, vacuum, lbf 20,000/13,500
13,500 750,000 235,100 Specific impulse, sea level, sec N/A N/A 341
N/A Specific impulse, vacuum, sec 393/469 469 383.7 462.9 Chamber
pressure, psia 2,700/1,800 1,800 5,000/2,500 2,500 Oxidizer:Fuel
ratio 1.7/7.0 7.0 3.2/6.0 6.0 Nozzle expansion ratio 400 400
74.8/36.3 119.9 Engine dry mass, lbm Fixed nozzle 310 270 8,127
8,127 Rolling nozzle 340 300 N/A N/A
[0032] The embodiment shown in FIG. 9 concept uses dual-fuel "space
engines" as shown in FIG. 8 and preferably combines four novel
features: 1) ventral propulsion; 2) assembly in MTO; 3) reverse use
of dual-fuel engines; and 4) use of skids for Moon and Earth
landing, reducing weight, complexity and vulnerability to
mechanical clogging by Moon dust. Reverse use of dual-fuel engines
(i.e. reversing the burn sequence of the "space engines" as defined
in FIG. 8 and Table 9 from the typical first burn of monomethyl
hydrazine (MMH) and subsequent hydrogen (H.sub.2) burn to instead
burn H.sub.2 first, then MMH, offers the improvement of extending
mission stay time on the lunar surface. This is because the MMH
tank can be insulated to essentially eliminate boiloff, which is
not true for H2 under lunar surface temperature and vacuum
conditions. Thus the hydrogen is exhausted for Moon landing, so
that only storable propellants remain for Moon liftoff and escape
and hydrogen boiloff is avoided during Moon surface stay time. As
used throughout the specification and claims, the term "reverse use
mode" means a dual fuel engine burning a first fuel during landing
on the moon, the first fuel subject to boiloff on the lunar
surface, and saving a second fuel for lunar take off and escape,
the second fuel stored in tanks insulated to prevent boiloff of the
second fuel on the lunar surface. The embodiment shown in FIG. 10
also uses the dual-fuel "space engines" for the geolunar shuttle
stage and existing single fuel engines for the RGL. Both stages are
fully reusable. The embodiment shown in FIG. 11 uses both axial and
ventral dual-fuel "space engines" for the geolunar shuttle stage as
shown in FIG. 8 and Table 9, scaled up to provide forty percent
more thrust, and dual-fuel "liftoff engines" for the RGL. Vehicle
parameters for the embodiments shown in FIGS. 9A, 10, and 11 are
listed in Tables 10-12, respectively.
TABLE-US-00010 TABLE 10 VEHICLE ELEMENT EXTERNAL PARAMETER CORE
TANKS Personnel (4) 1,000 -- ECLSS (10 days) 2,000 -- Mission
equipment 2,000 -- Gross start weight, lbm 64,700 30,600 Dry
weight, lbm 18,200* -- Engines 4xO.sub.2/MMH/H.sub.2 1,200 Re-entry
planform loading, 26.8 -- (w/4 crew), lbm ft.sup.2 Re-entry cross
range, n mi. .+-.4,500 -- *Incl. 15% margin
TABLE-US-00011 TABLE 11 VEHICLE REUSABLE GLOBAL GEOLUNAR PARAMETER
LAUNCHER SHUTTLE Payload capability.sup.a, lbm 302,000 (nom.) Crew
(6), lbm -- 1,500 Mission equipt., lbm -- 1,000 Gross liftoff mass,
lbm 7,305,318 301,001 Dry mass less engines.sup.b, lbm 368,460
30,841 Engines (lbm) 8xRD-180 48,060 -- 6xRS-25 43,218 --
4xDF(O.sub.2/MMH/H.sub.2); F.sub.vac = 13.5 Klbm -- 1,360 Re-entry
planform loading, lbm/ft.sup.2 30.1 17.1 Return glide downrange, n
mi. (global) (global) Return glide crossrange, n mi. .+-.3,500
.sup.a50 .times. 100 n mi., 28.7.degree.; .sup.bIncl. 15%
margin
TABLE-US-00012 TABLE 12 VEHICLE GEOLUNAR SHUTTLE REUSABLE GLOBAL
LAUNCHER DROP PARAMETER CORE CORE TANKS (2) Payload
capability.sup.a, lbm 735,000 (nom.) -- -- -- Crew (2), lbm -- --
500 -- Cargo, Earth.fwdarw.Moon.return, lbm -- -- 50,000/35,000 --
Gross liftoff mass, lbm 7,099,778 2,731,305 726,866 408,076 Dry
mass less engines.sup.b, lbm 382,430 109,900 51,270 15,318 Engines,
lbm 19xDF/DX(O.sub.2/C.sub.3H.sub.8/H.sub.2); F.sub.sl = 750 Klbm
154,473 -- -- -- 4xDF(O.sub.2/MMH/H.sub.2); F.sub.vac = 13.5 Klbm
-- -- 1,870 -- 4xDF(O.sub.2/H.sub.2 version); F.sub.vac = 19 Klbm
-- -- 1,650 -- Re-entry planform loading, lbm/ft.sup.2 31.8 -- 14.1
-- Cargo bay, ft -- -- 15 .times. 40 -- Cargo density, lbm/ft.sup.3
-- -- 7.1/5.0 -- Return glide downrange, n mi. (global) -- (global)
-- Return glide crossrange, n mi. .+-.3,500 -- .+-.4,500 --
.sup.a50 .times. 100 n mi., 28.7.degree.; .sup.bIncl. 15%
margin
[0033] Embodiments of the geolunar shuttle of the present invention
preferably utilize controllable throttling. To attain descent and
ascent trajectories through the lunar gravity field, and soft
landing at a precisely selected target site, the vehicle preferably
comprises specialized electronic hardware and software to control
throttleable main engines, such as the RL10-B2. There is preferably
a provision for manual override for emergencies, and the system
preferably enables final adjustments during touchdown. A
controllable throttling system is typically not needed for vehicles
not landing on the moon.
[0034] Although the invention has been described in detail with
particular reference to the disclosed embodiments, other
embodiments can achieve the same results. Variations and
modifications of the present invention will be obvious to those
skilled in the art and it is intended to cover all such
modifications and equivalents. The entire disclosures of all
patents, references, and publications cited above are hereby
incorporated by reference.
* * * * *